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Hypergolic azide fuels with hydrogen peroxide

a hydrogen peroxide and hydrogen azide technology, applied in the direction of pressure gas generation, explosives, weapons, etc., can solve the problems of unstable fuel and oxidizer, and the flash point of methanol is too low to be considered for some military applications

Inactive Publication Date: 2005-09-27
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a new type of propellant that can be used in hypergolic bi-propellant propulsion systems. This propellant contains an azide compound and a catalyst made of a transition metal compound. The oxidizer composition contains hydrogen peroxide in water. When these two components are mixed, they spontaneously ignite and produce thrust. The technical effect of this invention is to provide a more efficient and reliable propellant for use in hypergolic bi-propellant propulsion systems.

Problems solved by technology

In such bi-propellant mixtures, the fuel and the oxidizer are unstable when mixed together and are generally stored separately.
For example, the flash point of methanol is too low to be considered for some military applications.

Method used

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  • Hypergolic azide fuels with hydrogen peroxide
  • Hypergolic azide fuels with hydrogen peroxide
  • Hypergolic azide fuels with hydrogen peroxide

Examples

Experimental program
Comparison scheme
Effect test

example 1

[0027]Open face single element injector tests were performed using a fuel composition containing 85% by volume DMAZ and 15% by volume Cobalt Hex-Cem containing 12% cobalt ethylhexanoate in mineral spirits. The mixture contained 1.2% by weight cobalt metal. The oxidizer stream consisted of 90% by weight hydrogen peroxide in water. A fuel lead of 100 msec was used. The oxidizer to fuel ratio varied during the testing from 2 to 4. The fuel ignited late, away from the injector face at about 100 msec ignition delay. The drop test corresponding to this mixture using 90% by weight hydrogen peroxide resulted in an ignition delay of less than 16 msec.

example 2

[0028]A drop test was carried out with a fuel composition containing 97.3% by volume DMAZ and 2.7% by volume Cobalt Hex-Cem catalyst. The mixture contained 0.2% by weight cobalt metal. The drop test ignition delay of this fuel combination with 85% by weight hydrogen peroxide was less than 48 msec.

example 3

[0029]A drop test was carried out with a fuel composition containing 60% by volume JP-10, 27% by volume DMAZ and 13% by volume Cobalt Hex-Cem catalyst. The mixture contained 1.0% by weight cobalt metal. The drop test ignition delay of this fuel combination with 88% by weight hydrogen peroxide was less than 32 msec.

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Abstract

Hypergolic fuel propulsion systems contain a fuel composition and an oxidizer composition. The fuel composition contains an azide compound that has at least one tertiary nitrogen and at least one azide functional group, as well as a catalyst that contains at least one transition metal compound. The fuel composition optionally further contains a hydrocarbon fuel. The oxidizer composition contains hydrogen peroxide. The transition metal catalyst is preferably selected from the group consisting of compounds of cobalt and manganese. The invention provides a method for propelling a vehicle by providing a fuel mixture that spontaneously ignites with the oxidizer composition in an engine to provide thrust.

Description

FIELD OF THE INVENTION[0001]The present invention relates to hypergolic azide fuels with hydrogen peroxide. More specifically, the invention provides fuels containing azide compounds and transition metal catalysts that spontaneously ignite on contact with an oxidizer composition.BACKGROUND OF THE INVENTION[0002]Chemical fuels release their energy when combined with an oxidizing composition in such a way that a spontaneous chemical reaction occurs. In the case of conventional fuels for land vehicles, the fuel is a hydrocarbon mixture such as gasoline or diesel fuel and the oxidizing composition is air. The fuel burns in the presence of air when initiated by, for example, a spark in an internal combustion engine. For applications requiring higher energy output or thrust, such as rocket or missile propulsion systems, bi-propellant fuel mixtures are generally used. In such bi-propellant mixtures, the fuel and the oxidizer are unstable when mixed together and are generally stored separat...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): C06D5/00C06B47/00C06D5/08C06B47/02
CPCC06B47/02C06D5/08
Inventor HALLIT, RAMONA E. A.BAUERLE, GEORGE
Owner THE BOEING CO